def setup_cb(comm):
solver = ADFLOW(options=options, comm=comm, debug=False)
solver.addFamilyGroup('upstream',['INFLOW'])
solver.addFamilyGroup('downstream',['OUTFLOW'])
solver.addFamilyGroup('all_flow',['INFLOW', 'OUTFLOW'])
solver.addFunction('mdot', 'upstream', name="mdot_up")
solver.addFunction('mdot', 'downstream', name="mdot_down")
solver.addFunction('mavgptot', 'downstream', name="mavgptot_down")
solver.addFunction('mavgptot', 'upstream', name="mavgptot_up")
solver.addFunction('aavgptot', 'downstream', name="aavgptot_down")
solver.addFunction('aavgptot', 'upstream', name="aavgptot_up")
solver.addFunction('mavgttot', 'downstream', name="mavgttot_down")
solver.addFunction('mavgttot', 'upstream', name="mavgttot_up")
solver.addFunction('mavgps', 'downstream', name="mavgps_down")
solver.addFunction('mavgps', 'upstream', name="mavgps_up")
solver.addFunction('aavgps', 'downstream', name="aavgps_down")
solver.addFunction('aavgps', 'upstream', name="aavgps_up")
solver.addFunction('mavgmn', 'downstream', name="mavgmn_down")
solver.addFunction('mavgmn', 'upstream', name="mavgmn_up")
solver.addFunction('drag', 'all_flow', name="thrust") # this naming makes it seem like wishful thinking
solver.addFunction('dragpressure', 'all_flow', name="thrust_pressure")
solver.addFunction('dragviscous', 'all_flow', name="thrust_viscous")
solver.addFunction('dragmomentum', 'all_flow', name="thrust_momentum")
return solver, None, None, None
def setup_cb(comm):
solver = ADFLOW(options=options, comm=comm, debug=True)
solver.addIntegrationSurface('../inputFiles/integration_plane_viscous.fmt',
'viscous_plane')
solver.finalizeUserIntegrationSurfaces()
solver.addFamilyGroup('upstream', ['inlet'])
solver.addFamilyGroup('downstream', ['outlet'])
solver.addFamilyGroup('all_flow', ['inlet', 'outlet'])
solver.addFamilyGroup('output_fam', ['all_flow', 'allWalls'])
solver.addFunction('mdot', 'upstream', name="mdot_up")
solver.addFunction('mdot', 'downstream', name="mdot_down")
solver.addFunction('mdot', 'viscous_plane', name="mdot_plane")
solver.addFunction('mavgptot', 'downstream', name="mavgptot_down")
solver.addFunction('mavgptot', 'upstream', name="mavgptot_up")
solver.addFunction('mavgptot', 'viscous_plane', name="mavgptot_plane")
solver.addFunction('aavgptot', 'downstream', name="aavgptot_down")
solver.addFunction('aavgptot', 'upstream', name="aavgptot_up")
solver.addFunction('aavgptot', 'viscous_plane', name="aavgptot_plane")
solver.addFunction('mavgttot', 'downstream', name="mavgttot_down")
solver.addFunction('mavgttot', 'upstream', name="mavgttot_up")
solver.addFunction('mavgttot', 'viscous_plane', name="mavgttot_plane")
solver.addFunction('mavgps', 'downstream', name="mavgps_down")
solver.addFunction('mavgps', 'upstream', name="mavgps_up")
solver.addFunction('mavgps', 'viscous_plane', name="mavgps_plane")
solver.addFunction('aavgps', 'downstream', name="aavgps_down")
solver.addFunction('aavgps', 'upstream', name="aavgps_up")
solver.addFunction('aavgps', 'viscous_plane', name="aavgps_plane")
solver.setOption('ncycles', 1000)
return solver, None, None, None
class TestSolveIntegrationPlane(reg_test_classes.RegTest):
"""
Tests that ADflow can converge the wing from the mdo tutorial using the euler
equation to the required accuracy as meassure by the norm of the residuals,
and states, and the accuracy of the functions
based on the old regression test
Test 9: MDO tutorial -- Euler -- Solution Test
"""
N_PROCS = 2
options = {
"gridfile":
os.path.join(baseDir, "../../input_files/conic_conv_nozzle_mb.cgns"),
"outputdirectory":
os.path.join(baseDir, "../output_files"),
# Physics Parameters
"equationType":
"Euler",
"smoother":
"DADI",
"nsubiter":
3,
"CFL":
4.0,
"CFLCoarse":
1.25,
"MGCycle":
"3w",
"MGStartLevel":
-1,
"nCyclesCoarse":
250,
"nCycles":
1000,
"monitorvariables": ["cpu", "resrho", "cl", "cd"],
"volumevariables": ["blank"],
"surfacevariables": ["mach", "cp", "vx", "vy", "vz", "blank"],
"useNKSolver":
True,
"nkswitchtol":
0.01,
"nkadpc":
True,
"nkjacobianlag":
5,
"nkouterpreconits":
3,
"nkinnerpreconits":
2,
# Convergence Parameters
"L2Convergence":
1e-10,
"L2ConvergenceCoarse":
1e-2,
"adjointl2convergence":
1e-6,
"forcesAsTractions":
True,
"debugzipper":
True,
"nearwalldist":
0.001,
# 'nkls':'none',
"solutionprecision":
"double",
"adjointsubspacesize":
200,
"outerpreconits":
3,
"zipperSurfaceFamily":
"output_fam",
"flowtype":
"internal",
}
ref_file = "solve_conic_mb.json"
def setUp(self):
super().setUp()
self.ap = copy.copy(ap_conic_conv_nozzle)
options = copy.copy(adflowDefOpts)
options.update(self.options)
# Setup aeroproblem
planeFile = os.path.join(
baseDir, "../../input_files/integration_plane_viscous.fmt")
options = copy.copy(adflowDefOpts)
options.update(self.options)
# Setup aeroproblem
self.ap.evalFuncs.extend([
"mdot_plane", "mavgptot_plane", "aavgptot_plane", "mavgttot_plane",
"mavgps_plane", "aavgps_plane"
])
# Create the solver
self.CFDSolver = ADFLOW(options=options, debug=False)
self.CFDSolver.addIntegrationSurface(planeFile, "viscous_plane")
self.CFDSolver.finalizeUserIntegrationSurfaces()
self.CFDSolver.addFamilyGroup("upstream", ["inlet"])
self.CFDSolver.addFamilyGroup("downstream", ["outlet"])
self.CFDSolver.addFamilyGroup("all_flow", ["inlet", "outlet"])
self.CFDSolver.addFamilyGroup("output_fam", ["all_flow", "allWalls"])
self.CFDSolver.addFunction("mdot", "upstream", name="mdot_up")
self.CFDSolver.addFunction("mdot", "downstream", name="mdot_down")
self.CFDSolver.addFunction("mdot", "viscous_plane", name="mdot_plane")
self.CFDSolver.addFunction("mavgptot",
"downstream",
name="mavgptot_down")
self.CFDSolver.addFunction("mavgptot", "upstream", name="mavgptot_up")
self.CFDSolver.addFunction("mavgptot",
"viscous_plane",
name="mavgptot_plane")
self.CFDSolver.addFunction("aavgptot",
"downstream",
name="aavgptot_down")
self.CFDSolver.addFunction("aavgptot", "upstream", name="aavgptot_up")
self.CFDSolver.addFunction("aavgptot",
"viscous_plane",
name="aavgptot_plane")
self.CFDSolver.addFunction("mavgttot",
"downstream",
name="mavgttot_down")
self.CFDSolver.addFunction("mavgttot", "upstream", name="mavgttot_up")
self.CFDSolver.addFunction("mavgttot",
"viscous_plane",
name="mavgttot_plane")
self.CFDSolver.addFunction("mavgps", "downstream", name="mavgps_down")
self.CFDSolver.addFunction("mavgps", "upstream", name="mavgps_up")
self.CFDSolver.addFunction("mavgps",
"viscous_plane",
name="mavgps_plane")
self.CFDSolver.addFunction("aavgps", "downstream", name="aavgps_down")
self.CFDSolver.addFunction("aavgps", "upstream", name="aavgps_up")
self.CFDSolver.addFunction("aavgps",
"viscous_plane",
name="aavgps_plane")
def test_solve(self):
# do the solve
self.CFDSolver(self.ap)
# check its accuracy
utils.assert_functions_allclose(self.handler,
self.CFDSolver,
self.ap,
tol=1e-9)
utils.assert_states_allclose(self.handler, self.CFDSolver, tol=1e-10)
utils.assert_residuals_allclose(self.handler,
self.CFDSolver,
self.ap,
tol=1e-10)
class TestSolveOverset(reg_test_classes.RegTest):
"""
Tests that ADflow can converge the wing from the mdo tutorial using the euler
equation to the required accuracy as meassure by the norm of the residuals,
and states, and the accuracy of the functions
based on the old regression test 17 and 18
"""
N_PROCS = 2
options = {
"gridfile":
os.path.join(baseDir, "../../input_files/conic_conv_nozzle.cgns"),
"outputdirectory":
os.path.join(baseDir, "../output_files"),
# Physics Parameters
"equationType":
"Euler",
"smoother":
"DADI",
"nsubiter":
3,
"CFL":
4.0,
"CFLCoarse":
1.25,
"MGCycle":
"sg",
"MGStartLevel":
-1,
"nCyclesCoarse":
250,
"nCycles":
1000,
"monitorvariables": ["cpu", "resrho", "cl", "cd"],
"volumevariables": ["blank"],
"surfacevariables": ["mach", "cp", "vx", "vy", "vz", "blank"],
"useNKSolver":
True,
"nkswitchtol":
0.01,
"nkadpc":
True,
"nkjacobianlag":
5,
"nkouterpreconits":
3,
"nkinnerpreconits":
2,
# Convergence Parameters
"L2Convergence":
1e-10,
"L2ConvergenceCoarse":
1e-4,
"adjointl2convergence":
1e-6,
"forcesAsTractions":
True,
"debugzipper":
True,
"nearwalldist":
0.001,
# 'nkls':'none',
"solutionprecision":
"double",
"adjointsubspacesize":
200,
"outerpreconits":
3,
"zipperSurfaceFamily":
"output_fam",
"flowtype":
"internal",
"blocksplitting":
True,
}
ap = copy.copy(ap_conic_conv_nozzle)
ref_file = "solve_conic_overset.json"
def setUp(self):
super().setUp()
options = copy.copy(adflowDefOpts)
options.update(self.options)
# Setup aeroproblem
self.ap.setBCVar("Pressure", 79326.7, "downstream")
self.ap.addDV("Pressure", family="downstream")
self.ap.setBCVar("PressureStagnation", 100000.0, "upstream")
self.ap.addDV("PressureStagnation", family="upstream")
self.ap.setBCVar("TemperatureStagnation", 500.0, "upstream")
self.ap.addDV("TemperatureStagnation", family="upstream")
# Create the solver
self.CFDSolver = ADFLOW(options=options, debug=False)
self.CFDSolver.addFamilyGroup("upstream", ["inlet"])
self.CFDSolver.addFamilyGroup("downstream", ["outlet"])
self.CFDSolver.addFamilyGroup("all_flow", ["inlet", "outlet"])
self.CFDSolver.addFamilyGroup("output_fam", ["all_flow", "allWalls"])
self.CFDSolver.addFunction("mdot", "upstream", name="mdot_up")
self.CFDSolver.addFunction("mdot", "downstream", name="mdot_down")
self.CFDSolver.addFunction("mavgptot",
"downstream",
name="mavgptot_down")
self.CFDSolver.addFunction("mavgptot", "upstream", name="mavgptot_up")
self.CFDSolver.addFunction("aavgptot",
"downstream",
name="aavgptot_down")
self.CFDSolver.addFunction("aavgptot", "upstream", name="aavgptot_up")
self.CFDSolver.addFunction("mavgttot",
"downstream",
name="mavgttot_down")
self.CFDSolver.addFunction("mavgttot", "upstream", name="mavgttot_up")
self.CFDSolver.addFunction("mavgps", "downstream", name="mavgps_down")
self.CFDSolver.addFunction("mavgps", "upstream", name="mavgps_up")
self.CFDSolver.addFunction("aavgps", "downstream", name="aavgps_down")
self.CFDSolver.addFunction("aavgps", "upstream", name="aavgps_up")
def test_solve(self):
# do the solve
self.CFDSolver(self.ap)
# check its accuracy
utils.assert_functions_allclose(self.handler,
self.CFDSolver,
self.ap,
tol=1e-9)
utils.assert_states_allclose(self.handler, self.CFDSolver, tol=1e-10)
# Check the residual
res = self.CFDSolver.getResidual(self.ap)
totalR0 = self.CFDSolver.getFreeStreamResidual(self.ap)
res /= totalR0
reducedSum = self.CFDSolver.comm.reduce(np.sum(res**2))
if self.CFDSolver.comm.rank == 0:
self.assertLessEqual(np.sqrt(reducedSum),
self.options["L2Convergence"])
class TestSolve(reg_test_classes.RegTest):
"""
Tests that ADflow can converge the wing from the mdo tutorial using the euler
equation to the required accuracy as meassure by the norm of the residuals,
and states, and the accuracy of the functions
based on the old regresson test 16
"""
N_PROCS = 2
ref_file = "solve_2D_conv_nozzle.json"
options = {
"gridfile": os.path.join(baseDir, "../../input_files/euler_conv_nozzle.cgns"),
"solutionprecision": "double",
"gridprecision": "double",
"liftIndex": 2,
"CFL": 3.0,
"CFLCoarse": 1.5,
"MGCycle": "2w",
"MGStartLevel": 2,
"nCyclesCoarse": 500,
"nCycles": 2500,
"monitorvariables": ["resrho", "cl", "cd", "yplus"],
"nsubiterturb": 3,
"useNKSolver": True,
"NKSubSpaceSize": 60,
"L2Convergence": 1e-14,
"L2ConvergenceCoarse": 1e-2,
"NKSwitchTol": 1e-2,
"nkadpc": False,
"vis4": 0.006,
"vis2": 0.0,
"blocksplitting": True,
"solutionPrecision": "double",
"flowtype": "internal",
}
ap = ap_2D_conv_nozzle
def setUp(self):
super().setUp()
options = copy.copy(adflowDefOpts)
options["outputdirectory"] = os.path.join(baseDir, options["outputdirectory"])
options.update(self.options)
# Create the solver
self.CFDSolver = ADFLOW(options=options, debug=False)
self.CFDSolver.addFamilyGroup("upstream", ["INFLOW"])
self.CFDSolver.addFamilyGroup("downstream", ["OUTFLOW"])
self.CFDSolver.addFamilyGroup("all_flow", ["INFLOW", "OUTFLOW"])
self.CFDSolver.addFunction("mdot", "upstream", name="mdot_up")
self.CFDSolver.addFunction("mdot", "downstream", name="mdot_down")
self.CFDSolver.addFunction("mavgptot", "downstream", name="mavgptot_down")
self.CFDSolver.addFunction("mavgptot", "upstream", name="mavgptot_up")
self.CFDSolver.addFunction("aavgptot", "downstream", name="aavgptot_down")
self.CFDSolver.addFunction("aavgptot", "upstream", name="aavgptot_up")
self.CFDSolver.addFunction("mavgttot", "downstream", name="mavgttot_down")
self.CFDSolver.addFunction("mavgttot", "upstream", name="mavgttot_up")
self.CFDSolver.addFunction("mavgps", "downstream", name="mavgps_down")
self.CFDSolver.addFunction("mavgps", "upstream", name="mavgps_up")
self.CFDSolver.addFunction("aavgps", "downstream", name="aavgps_down")
self.CFDSolver.addFunction("aavgps", "upstream", name="aavgps_up")
self.CFDSolver.addFunction("mavgmn", "downstream", name="mavgmn_down")
self.CFDSolver.addFunction("mavgmn", "upstream", name="mavgmn_up")
self.CFDSolver.addFunction("drag", "all_flow", name="thrust") # this naming makes it seem like wishful thinking
self.CFDSolver.addFunction("dragpressure", "all_flow", name="thrust_pressure")
self.CFDSolver.addFunction("dragviscous", "all_flow", name="thrust_viscous")
self.CFDSolver.addFunction("dragmomentum", "all_flow", name="thrust_momentum")
def test_solve(self):
# do the solve
self.CFDSolver(self.ap)
# check if solution failed
self.assert_solution_failure()
# check its accuracy
utils.assert_functions_allclose(self.handler, self.CFDSolver, self.ap, tol=1e-9)
utils.assert_states_allclose(self.handler, self.CFDSolver, tol=1e-10)
utils.assert_residuals_allclose(self.handler, self.CFDSolver, self.ap, tol=1e-10)
